CN110748437B - Propellant conveying system - Google Patents
Propellant conveying system Download PDFInfo
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- CN110748437B CN110748437B CN201910891164.0A CN201910891164A CN110748437B CN 110748437 B CN110748437 B CN 110748437B CN 201910891164 A CN201910891164 A CN 201910891164A CN 110748437 B CN110748437 B CN 110748437B
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- pipe
- gas
- propellant
- pneumatic pump
- pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Abstract
The invention discloses a propellant delivery system, comprising a storage tank for storing propellant; the first end of the conveying pipe is connected with the discharge hole of the storage box, and the second end of the conveying pipe is connected with the feed inlet of the engine; the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant; a high pressure gas section for storing high pressure gas; the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump; the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe; and the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank. The invention improves the conveying pressure of the propellant, and pressurizes the storage tank, so that the whole pressurizing conveying system has small volume and light weight.
Description
Technical Field
The invention belongs to the field of fuel conveying, and particularly relates to a propellant conveying system.
Background
Rocket engines rely on propellant for operation and the pressure of the propellant entering the engine needs to be high, so a delivery system is required to increase the inlet pressure of the propellant into the engine.
Rocket engine conveying systems generally work by utilizing a self-generated pressurization system, namely, a propellant storage tank of the same type is pressurized by utilizing gas formed by heating and evaporating the propellant.
However, when the requirement for the inlet pressure of the engine is higher in the face of a complex flight mission, the autogenous pressurization system cannot meet the requirement, the requirement for the high inlet pressure of the engine causes the mass of the pressurized gas and the large scale of the pressurization conveying system, the weight of the storage box structure is increased, and the structural efficiency of the carrier rocket is reduced.
Disclosure of Invention
In order to solve the problems, the invention provides a propellant conveying system, which aims to solve the technical problems of increasing the conveying pressure of the propellant and pressurizing a storage tank.
The technical scheme of the invention is as follows:
a propellant delivery system comprising:
a tank for storing a propellant;
the first end of the conveying pipe is connected to the discharge hole of the storage box, and the second end of the conveying pipe is connected to the feed inlet of the engine;
the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant;
a high pressure gas section for storing high pressure gas;
the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump;
the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe;
and the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank.
The conveying pressure of the propellant is improved, the pressurization requirement on the storage tank is met, the weight and the volume of the whole system are reduced, and the pneumatic pump is safe and reliable.
According to an embodiment of the present invention, the system includes a pre-cooling system, and the pre-cooling system includes:
the first end of the return pipe is connected with the feed port of the storage tank;
a first inlet of the backflow control valve is connected with the second end of the conveying pipe, a first outlet of the backflow control valve is connected with a feed port of the engine, and a second outlet of the backflow control valve is connected with the second end of the backflow pipe;
the first end of the pre-cooling pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-cooling pipe is connected with the air inlet of the pneumatic pump;
and the pre-cooling pipe control part is arranged on the pre-cooling pipe and used for opening and closing a gas channel in the pre-cooling pipe.
The engine can be circularly precooled, the normal work of the engine is ensured, the propellant can flow back, and the utilization rate is improved.
According to an embodiment of the present invention, the pre-cooling pipe control part is a pre-cooling solenoid valve. The electromagnetic valve is a common gas on-off control element, and is simple and practical.
According to an embodiment of the invention, the pre-cooling system comprises a pre-cooling gas pressure reducing device, wherein the pre-cooling gas pressure reducing device is arranged on the pre-cooling pipe between the pre-cooling electromagnetic valve and the pneumatic pump.
According to an embodiment of the present invention, the precooling gas pressure reducing device includes a first pressure reducing valve and a first orifice plate, and the first pressure reducing valve and the first orifice plate are sequentially disposed on the precooling pipe between the precooling solenoid valve and the pneumatic pump. The pressure reducing valve and the perforated plate are common pressure reducing devices, and realize pressure reduction and steady flow of gas.
According to an embodiment of the present invention, the first pressure reducing valve is an automatic adjusting pressure reducing valve, and the first orifice plate is a bowl-shaped structure.
According to an embodiment of the present invention, the pre-pressure pipe control portion is a pre-pressure solenoid valve. The electromagnetic valve is a common gas on-off control element, and is simple and practical.
According to an embodiment of the present invention, the pneumatic pump further comprises a pre-compressed gas pressure reducing device, and the pre-compressed gas pressure reducing device is disposed on the pre-compressed pipe between the pre-compressed solenoid valve and the pneumatic pump.
According to an embodiment of the present invention, the pre-pressurized gas pressure reducing device includes a second pressure reducing valve and a second orifice plate, and the second pressure reducing valve and the second orifice plate are sequentially disposed on the pre-pressurized pipe between the pre-pressurized solenoid valve and the pneumatic pump. The pressure reducing valve and the perforated plate are common pressure reducing devices, and realize pressure reduction and steady flow of gas.
According to an embodiment of the present invention, the second pressure reducing valve is an automatic adjusting pressure reducing valve, and the second orifice plate is a bowl-shaped structure.
According to one embodiment of the invention, the storage tank and the conveying pipe are both of metal thin-wall structures, and the outer walls of the storage tank and the conveying pipe are both provided with heat insulation layers. The metal thin-wall structure can reduce the weight.
According to an embodiment of the invention, the pressure inlet pipe is of a metal thin-wall structure. The metal thin-wall structure can reduce the weight.
According to an embodiment of the present invention, the return pipe is a metal thin-wall structure. The metal thin-wall structure can reduce the weight.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
(1) in one embodiment of the invention, the pneumatic pump is arranged to convey the propellant, the gas at the gas outlet of the pneumatic pump is conveyed into the storage tank through the pressurization pipe and is used for pressurizing the propellant, the conveying pressure of the propellant is improved, the pressurization requirement on the storage tank is realized, the gas after the pneumatic pump is recycled and utilized for pressurizing the storage tank, the high-efficiency utilization of the gas is realized, special pressurization equipment is not required to be arranged for the storage tank independently, the weight and the volume of the whole system are further reduced, and the pneumatic pump is safe and reliable.
(2) In one embodiment of the invention, the precooling system is arranged and comprises a return pipe, a backflow control valve, a precooling pipe and a precooling control part, and the propellant circularly flows through the engine, so that the circulating precooling of the engine is realized, the normal work of the engine is ensured, the propellant can flow back, and the utilization rate is improved.
(3) In one embodiment of the invention, the precooling gas pressure reducing device and the prepressing gas pressure reducing device are arranged, so that the functions of reducing the pressure of the high-pressure gas and stabilizing the gas pressure are achieved.
Drawings
The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings, in which:
FIG. 1 is a schematic diagram of the overall construction of a propellant delivery system of the present invention;
description of reference numerals:
1: a storage tank; 2: a pneumatic pump; 3: a delivery pipe; 4: a return pipe; 5: a reflux control valve; 6: an engine; 7: a high pressure gas section; 8: a precooling electromagnetic valve; 9: prepressing the electromagnetic valve; 10: a first pressure reducing valve; 11: a second pressure reducing valve; 12: a first orifice plate; 13: a second orifice plate; 14: and (4) pressurizing the pipe.
Detailed Description
A propellant delivery system in accordance with the present invention is described in further detail below with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise ratio for the purpose of facilitating and distinctly aiding in the description of the embodiments of the invention.
Referring to fig. 1, the present invention provides a propellant delivery system comprising a tank 1 for storing a propellant, the tank 1 having a metal thin-walled structure and being light in weight, and having an outer wall coated with a thermal insulation layer for insulating external heat; the delivery pipe 3 is used for delivering a propellant to the engine 6, the engine 6 can be a liquid rocket engine adopting liquid oxygen kerosene, liquid oxygen liquid hydrogen or other low-temperature propellants, the first end of the delivery pipe 3 is connected with the discharge hole of the storage box 1, the second end of the delivery pipe 3 is connected with the feed hole of the engine 6, the delivery pipe 3 adopts a metal thin-wall structure, and a heat insulation layer is sprayed on the outer wall of the delivery pipe 3, so that the purposes of light weight and heat insulation are achieved; the pneumatic pump 2 is arranged on the conveying pipe 3 and used for conveying the propellant, the pneumatic pump 2 is safe and reliable, the pneumatic pump 2 is specifically a pneumatic turbine pump, the turbine is blown by driving gas to drive the pump to operate, and the pump drives liquid in the conveying pipe 3 to flow and improves the liquid pressure; the high-pressure gas part 7 is used for storing high-pressure gas, the high-pressure gas part 7 can be containers such as a high-pressure gas cylinder and the like, the high-pressure gas cylinder can be a gas cylinder with the volume of 60L and the pressure of 35Mpa, the number of the high-pressure gas cylinders is determined according to flight mission requirements, the high-pressure gas is used for driving the pneumatic pump 2, and the high-pressure gas is inert gas; the pre-pressing pipe is used for conveying high-pressure gas to the pneumatic pump 2 so as to generate high-pressure propelling agent to work for the engine 6, the first end of the pre-pressing pipe is connected with the gas outlet of the high-pressure gas part 7, the second end of the pre-pressing pipe is connected with the gas inlet of the pneumatic pump 2, and the pre-pressing pipe can also be of a metal thin-wall structure; the prepressing pipe control part is arranged on the prepressing pipe and used for opening and closing a gas channel in the prepressing pipe, the prepressing pipe control part can be a control element for controlling the on-off of the gas channel, such as a prepressing electromagnetic valve 9, the prepressing electromagnetic valve 9 is a normally closed two-position two-way electromagnetic valve, and the electromagnetic valve executes the on-off action according to an instruction; the pressure increasing pipe 14 is used for increasing pressure of the storage tank 1 and is also of a metal thin-wall structure, a first end of the pressure increasing pipe 14 is connected to an air outlet of the pneumatic pump 2, a second end of the pressure increasing pipe 14 is connected with an air inlet of the storage tank 1, gas passing through the pneumatic pump 2 is recycled, the air inlet of the storage tank 1 is arranged at the top of the storage tank 1, and the gas enters the top space of the storage tank 1 to apply pressure to the propellant. The system adopts a method of adding the pneumatic pump 2 to the delivery pipe 3 to improve the pressure delivered by the propellant, thereby reducing the requirement of the pressurization pressure of the storage tank 1, simultaneously, the driving gas of the pneumatic pump 2 returns to the storage tank 1 for pressurization, the pressurization function of the storage tank 1 is considered, and no additional equipment is required to be added.
The pre-cooling system is used for pre-cooling the engine 6 and comprises a return pipe 4, the return pipe 4 is of a metal thin-wall structure and is used for conveying the propellant pre-cooled by the engine 6 back to the bottom of the storage box 1, and the first end of the return pipe 4 is connected with a feeding hole of the storage box 1; a first inlet of the backflow control valve 5 is connected with a second end of the delivery pipe 3, a first outlet of the backflow control valve 5 is connected with a feed inlet of a combustion chamber of the engine 6, a second outlet of the backflow control valve 5 is connected with a second end of the backflow pipe 4, the backflow control valve 5 is a two-position three-way valve and is a built-in valve of the engine 6, one outlet of the backflow control valve 5 is connected with the backflow pipe 4, the other outlet of the backflow control valve is connected with the combustion chamber of the engine 6, the valve is kept normally open with the backflow pipe 4 when not acting, and the valve is switched to be connected with the combustion chamber of the engine 6 and disconnected with the backflow pipe 4 after acting; the precooling pipe is used for conveying gas, the first end of the precooling pipe is connected with the gas outlet of the high-pressure gas part 7, the second end of the precooling pipe is connected with the gas inlet of the pneumatic pump 2, and the precooling pipe is also of a metal thin-wall structure; the pre-cooling pipe control part is arranged on the pre-cooling pipe, is used for opening and closing a gas channel in the pre-cooling pipe, and can be a control element for controlling the on-off of the gas channel, such as a pre-cooling electromagnetic valve 8, and the like, wherein the pre-cooling electromagnetic valve 8 is a normally closed two-position two-way electromagnetic valve, and the electromagnetic valve executes the on-off action according to instructions. The forced circulation precooling of the engine 6 is completed by the aid of the pneumatic pump 2, the return pipe 4 does not need to flow back to the upper part of the storage tank 1, the length of a pipeline is reduced, the weight is reduced, the system can meet the circulation precooling requirement of the engine 6 in a low liquid level state when being started for multiple times, and the system has very strong functions.
Further, the device comprises a precooling gas pressure reducing device, and the precooling gas pressure reducing device is arranged on a precooling pipe between the precooling electromagnetic valve 8 and the pneumatic pump 2. The precooling gas pressure reducing device comprises a first pressure reducing valve 10 and a first pore plate 12, wherein the first pressure reducing valve 10 and the first pore plate 12 are sequentially arranged on a precooling pipe between the precooling electromagnetic valve 8 and the pneumatic pump 2. Since the engine 6 precools and does not need high-pressure propellant, the first pressure reducing valve 10 and the first orifice plate 12 reduce the gas flow to a smaller flow state and stabilize the flow, so that the pneumatic pump 2 runs at a low speed and the requirement of the engine 6 for circulating precooling on the pump is met.
Further, the first pressure reducing valve 10 is an automatic regulating pressure reducing valve, and the first orifice plate 12 is a bowl-shaped structure. The automatic regulating type pressure reducing valve can reduce the pressure of the high-pressure gas in the high-pressure gas part 7 to a required pressure and keep the gas pressure stable along with the reduction of the gas cylinder pressure; the first orifice plate 12 is a bowl-shaped structure, which is beneficial to throttling high-pressure gas, controlling the gas flow within a certain range, and determining the aperture of the first orifice plate 12 according to a flight mission.
Further, the device comprises a pre-pressing gas pressure reducing device, wherein the pre-pressing gas pressure reducing device is arranged on the pre-pressing pipe between the pre-pressing electromagnetic valve 9 and the pneumatic pump 2. The pre-pressing gas pressure reducing device comprises a second pressure reducing valve 11 and a second pore plate 13, wherein the second pressure reducing valve 11 and the second pore plate 13 are sequentially arranged on a pre-pressing pipe between the pre-pressing electromagnetic valve 9 and the pneumatic pump 2. The second pressure reducing valve 11 and the second orifice 13 control the gas flow to a higher flow state and stabilize the flow, so that the pneumatic pump 2 runs at a high speed to deliver high-pressure propellant, and the requirement of high-pressure propellant required when the engine 6 is ignited is met.
Further, the second pressure reducing valve 11 is an automatic adjusting type pressure reducing valve, and the second orifice plate 13 is a bowl-shaped structure. The automatic regulating type pressure reducing valve can reduce the pressure of the high-pressure gas in the high-pressure gas part 7 to a required pressure and keep the gas pressure stable along with the reduction of the gas cylinder pressure; the second orifice plate 13 is of a bowl-shaped structure, so that high-pressure gas throttling is facilitated, the gas flow is controlled within a certain range, and the aperture of the second orifice plate 13 is determined according to a flight task.
The following further illustrates the specific working of the present invention:
firstly, precooling an engine 6, controlling a precooling electromagnetic valve 8 to be opened, enabling high-pressure gas of a high-pressure gas part 7 to pass through the precooling electromagnetic valve 8 through a precooling pipe, then passing through a first pressure reducing valve 10 and a first pore plate 12, reducing the gas flow to a certain value, stabilizing the flow, then enabling the low-flow gas to pass through a pneumatic pump 2, then entering the top of a storage tank 1 through a pressure increasing pipe 14, enabling the pneumatic pump 2 to run at a low speed to drive propellant in the storage tank 1, enabling the low-pressure propellant to enter a backflow control valve 5, enabling the backflow control valve 5 to be arranged in the engine 6 so as to achieve precooling on the engine 6, closing one way of the backflow control valve 5 to a combustion chamber of the engine 6, opening one way to a backflow pipe 4, enabling the propellant to flow back to the storage tank 1 through the backflow pipe 4, and completing the whole precooling process.
When the rocket is ignited, the precooling electromagnetic valve 8 is controlled to be closed, the prepressing electromagnetic valve 9 is opened, high-pressure gas in the high-pressure gas part 7 passes through the prepressing electromagnetic valve 9 through the prepressing pipe, passes through the second reducing valve 11 and the second orifice plate 13, the gas flow is controlled to be a certain large flow, the flow is stabilized, then the large flow gas passes through the pneumatic pump 2 and enters the top of the storage tank 1 through the pressure increasing pipe 14, the storage tank 1 is pressurized to improve the output pressure of the propellant, the pneumatic pump 2 operates at high speed to drive the propellant in the storage tank 1, the high-pressure propellant enters the backflow control valve 5, one path of the backflow control valve 5 to a combustion chamber of the engine 6 is opened, one path to the backflow pipe 4 is closed, the propellant enters the combustion chamber, and the whole ignition process is completed.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (8)
1. A propellant delivery system, comprising:
a tank for storing a propellant;
the first end of the conveying pipe is connected to the discharge hole of the storage box, and the second end of the conveying pipe is connected to the feed inlet of the engine;
the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant;
a high pressure gas section for storing high pressure gas;
the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump;
the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe;
the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank;
the system comprises a precooling system, wherein the precooling system comprises:
the first end of the return pipe is connected with the feed port of the storage tank;
a first inlet of the backflow control valve is connected with the second end of the conveying pipe, a first outlet of the backflow control valve is connected with a feed port of the engine, and a second outlet of the backflow control valve is connected with the second end of the backflow pipe;
the first end of the pre-cooling pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-cooling pipe is connected with the air inlet of the pneumatic pump;
the pre-cooling pipe control part is arranged on the pre-cooling pipe and used for opening and closing a gas channel in the pre-cooling pipe; the pre-cooling pipe control part is a pre-cooling electromagnetic valve;
the precooling gas pressure reducing device is arranged on the precooling pipe between the precooling electromagnetic valve and the pneumatic pump;
the prepressing pipe control part is a prepressing electromagnetic valve;
the pneumatic control system comprises a prepressing gas pressure reducing device, wherein the prepressing gas pressure reducing device is arranged on a prepressing pipe between a prepressing electromagnetic valve and a pneumatic pump.
2. The propellant delivery system of claim 1 wherein the pre-cooled gas pressure relief device comprises a first pressure relief valve and a first orifice plate, the first pressure relief valve and the first orifice plate being sequentially disposed on the pre-cooling tube between the pre-cooling solenoid valve and the pneumatic pump.
3. The propellant delivery system of claim 2 wherein the first pressure relief valve is an automatically adjusting pressure relief valve and the first orifice plate is a bowl.
4. The propellant delivery system of claim 1 wherein the pre-pressurized gas relief device comprises a second relief valve and a second orifice plate, the second relief valve and the second orifice plate being sequentially disposed on the pre-pressurized tube between the pre-pressurized solenoid valve and the pneumatic pump.
5. The propellant delivery system of claim 4 wherein the second pressure relief valve is an automatically adjusting pressure relief valve and the second orifice plate is a bowl.
6. The propellant delivery system of claim 1 wherein the reservoir and the delivery tube are each of thin-walled metal construction, and the outer walls of the reservoir and the delivery tube are each provided with a layer of thermal insulation.
7. The propellant delivery system of claim 1 wherein the booster duct is a metal thin-walled structure.
8. The propellant delivery system of claim 1 wherein the return tube is of metal thin-walled construction.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910891164.0A CN110748437B (en) | 2019-09-20 | 2019-09-20 | Propellant conveying system |
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|---|---|---|---|
| CN201910891164.0A CN110748437B (en) | 2019-09-20 | 2019-09-20 | Propellant conveying system |
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| CN110748437A CN110748437A (en) | 2020-02-04 |
| CN110748437B true CN110748437B (en) | 2022-03-01 |
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| CN111963340B (en) * | 2020-08-04 | 2021-10-19 | 西安航天动力研究所 | Multi-starting system of pneumatic supercharging device of liquid rocket engine |
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| FR2921979B1 (en) * | 2007-10-08 | 2014-06-13 | Astrium Sas | DEVICE AND METHOD FOR PUMP MOTORIZATION FOR INTERNAL COMBUSTION ENGINE FUSE ENGINE |
| US9273634B2 (en) * | 2011-08-18 | 2016-03-01 | Patrick R. E. Bahn | Rocket stage and method of improving an existing rocket stage |
| EP3004616B1 (en) * | 2013-06-07 | 2019-11-13 | Aerojet Rocketdyne, Inc. | Stored pressure driven cycle |
| CN204679261U (en) * | 2015-05-11 | 2015-09-30 | 上海宇航系统工程研究所 | A kind of reduction valve, pressure governor pilot system |
| CN106567791B (en) * | 2016-11-08 | 2018-04-06 | 上海宇航系统工程研究所 | A kind of forced circulation chilldown system |
| CN109372655A (en) * | 2018-12-13 | 2019-02-22 | 西安航天动力研究所 | The pre- pressure charging system of gas-liquid parallel drive and method that high-altitude low entry pressure starts |
| CN110030115A (en) * | 2019-03-27 | 2019-07-19 | 上海宇航系统工程研究所 | A kind of propellant tank combination pressure charging system |
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